US20060016193A1 - Turbo-jet engine with a protective screen of the fuel manihold of a burner ring, the burner ring and the protective screen - Google Patents
Turbo-jet engine with a protective screen of the fuel manihold of a burner ring, the burner ring and the protective screen Download PDFInfo
- Publication number
- US20060016193A1 US20060016193A1 US11/177,297 US17729705A US2006016193A1 US 20060016193 A1 US20060016193 A1 US 20060016193A1 US 17729705 A US17729705 A US 17729705A US 2006016193 A1 US2006016193 A1 US 2006016193A1
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- United States
- Prior art keywords
- screen
- orifices
- manihold
- pair
- turbo
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
- F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
- F02K3/105—Heating the by-pass flow
- F02K3/11—Heating the by-pass flow by means of burners or combustion chambers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the invention relates to a turbo-jet engine including a re-heating channel of the primary gas flow, a burner ring and a protective screen of the fuel manihold of the burner ring.
- the invention also relates to a burner ring and a protective screen for the turbo-jet engine.
- Turbo-jet engines with after burner comprise generally from the upstream portion to the downstream portion, in the flow direction of the gases, one or several compressor stages, a combustion chamber, one or several turbine stages, a re-heating channel or after burner channel, and an ejection nozzle.
- the primary gas flow is compressed in the compressor stages, partakes of the combustion of the fuel in the combustion chamber, expands in the turbine stages and enables new combustion of fuel, thanks to the oxygen still present therein, in the re-heating channel before expanding in the ejection nozzle.
- the re-heating channel comprises generally, at input, flame holder arms, extending radially in the primary gas flow and comprises a fuel injector which sprays said fuel into the gas stream, downwardly.
- the fuel is ignited and the flames are, because of the sectional shape of the arms causing a depression, “held” in the walls of the arms.
- the ring comprises generally an outer enclosure in the form of a gutter, including a U-shaped section, open downward of the re-heating channel, in the gas stream of the primary flow, wherein a fuel manihold is situated, of circular section, seen as an axial sectional view, whereof the purpose is to spray the fuel downward.
- the fuel manihold Downstream of the manihold, the fuel is ignited, and the flame is held in the gutter of the ring because of the shape of the latter. Consequently, the re-circulations of gas in the enclosure of the gutter are re-circulations of very hot gases.
- the fuel manihold is surrounded by an anti-radiation screen.
- Such screen includes fuel passage orifices, corresponding to orifices of the manihold, generally gathered in twos, in a same axial plane, at regular angular positions on the ring.
- the purpose of the present invention is to improve the cooling process of the anti-radiation screen.
- the invention relates to a double flow turbo-jet engine, including one or several compressor stages, a combustion chamber, one or several turbine stages, a re-heating channel of the primary flow and an ejection nozzle, the secondary flow emerging at least partially in the primary flow upstream of the re-heating channel, the re-heating channel including a burner ring, containing a flame holder gutter in the form of a ring portion whereof the upstream section is situated in the secondary flow, receiving a fuel manihold and a protective tubular screen of the manihold, characterised in that the gutter includes an upstream recess linked with the secondary flow, and the screen includes, on its upstream section, at least one ventilation orifice of the space situated between the screen and the manihold.
- the ventilation means comprise at least one ventilation orifice situated on the upstream portion of the screen.
- the manihold including at least one pair of fuel spraying orifices
- the screen including at least one pair of corresponding orifices
- a ventilation orifice is drilled on the screen at the same angular position as the pair of orifices.
- the screen includes a plurality of pairs of orifices, it comprises a ventilation orifice drilled at the same angular position of each pair of orifices.
- the invention also relates to a burner ring for a turbo-jet engine, including a flame holder gutter, a fuel manihold and a protective screen of the manihold, characterised in that it comprises the features of the ring described previously.
- the invention still relates to a protective screen of a burner ring manihold for a turbo-jet engine, characterised in that it comprises at least one pair of orifices and a ventilation orifice situated in the transversal plane of the pair of orifices.
- the screen comprises a plurality of pairs of orifices and a ventilation orifice situated in the transversal plane of each pair of orifices.
- FIG. 1 shows a partial axial sectional view of the preferred embodiment of the turbo-jet engine of the invention, in the zone of the burner ring;
- FIG. 2 shows a partial cross-sectional view of the turbo-jet engine of the invention
- FIG. 3 shows a perspective view of the fuel manihold of the burner ring of the turbo-jet engine of the invention
- FIG. 4 shows a perspective view of the anti-radiation screen of the burner ring of the turbo-jet engine of the invention
- FIG. 5 shows an axial sectional view of the burner ring of the turbo-jet engine of the invention, in a plane not including any pairs of orifices and
- FIG. 6 shows an axial sectional view of the burner ring of the turbo-jet engine of the invention, in a plane including a pair of orifices.
- the turbo-jet engine of the invention extending globally along an axis A, comprises several compressor stages, a combustion chamber, several turbine stages, a re-heating channel of the primary flow 1 and an ejection nozzle.
- fuel injector arms 2 extend radially, whereof the purpose is to spray fuel towards the flame holder arms 3 , situated downstream of the fuel injector arms 2 and extending radially in the re-heating channel 1 .
- the secondary flow i.e. the cold air flow which has not run through the combustion chamber, emerges in the primary flow.
- a ferule 14 is placed upstream of the arms 3 and delineates a secondary flow channel 15 . Downstream of this ferule 14 , this secondary flow is mixed, at least partially, with the primary flow, in the re-heating channel 1 .
- the number of flame holder arms 3 is the same as that of the fuel injector arms 2 and are offset angularly relative to the latter, so that, on a front view, each fuel injector arm 2 is situated between two consecutive flame holder arms 3 , equidistant therefrom.
- the fuel injector arms 2 are radially smaller than the flame holder arms 3 .
- the flame holder arms 3 support a burner ring 4 .
- Such ring 4 is made of a plurality of portions of ring 4 ′, here nine in number, extending concentrically to the casing of the re-heating channel 1 , between two successive flame holder arms 3 . It will be referred below to the ring 4 , by which is meant in fact a portion of ring 4 ′, and the constitutive elements of the ring 4 will be in such a case elements constituting a portion of ring 4 ′, and therefore only extending on a truncated ring and not along a closed annular circumference.
- the fuel injector arms 2 extend radially, perpendicular to the axis of the turbo-jet engine.
- the flame holder arms 3 extend radially, tilted downward, from their base, relative to the perpendicular to the axis of the turbo-jet engine contained in the axial plane of the arms 3 .
- the fuel injector arms 2 spray fuel downward.
- the flame holder arms 3 do the same, and ensure moreover the ignition of the fuel and the catching of the flames by its outer walls, sized accordingly.
- the burner ring 4 includes a flame holder gutter 5 , delineating its open external enclosure, which exhibits on an axial sectional view, a U-shaped section, whereof the legs are turned downward.
- the gutter extends along an annular direction, or generatrix.
- the external leg of the U is greater than the internal leg, and the legs of the U are not parallel; it rather looks like a rounded base V; it will be referred to later as a U-shaped section.
- the gutter 5 is placed outside, just downstream of the ferule 14 .
- the upstream wall forming the base of its U-shaped section is in contact with the secondary cold flow, as well as its downstream walls forming the legs of its U-shaped section, whereof the purpose is to catch the flames of the re-heating channel 1 , are subjected directly to the heat thereof.
- the gutter 5 receives a fuel manihold 6 , of circular section, seen as an axial sectional view and matching the circumferential shape of the gutter 5 .
- the manihold 6 is supplied with fuel by a longitudinal feeding ductwork 7 , connected thereto from its upstream side. With reference to FIG. 6 , it comprises, arranged at regular angular positions, pairs of circular orifices 8 , 8 ′ for fuel spraying.
- the orifices of a same pair of orifices 8 , 8 ′ are situated on the same axial plane and are symmetrical relative to one another with respect to the plane perpendicular to said axial plane, parallel to the axis A of the turbo-jet engine and intersecting the section of the manihold 6 , at the angular position of the orifices 8 , 8 ′, into two equal semi-circles.
- the orifices 8 , 8 ′ are situated in the downstream portion of the fuel manihold 6 .
- the manihold 6 is enveloped in a anti-radiation screen 9 , of same tubular shape as the manihold 6 but whereof the section forms a circle of larger diameter, whereof the purpose is to protect the manihold 6 from the radiations of the flames situated downstream, here caught by the walls corresponding to the legs of the U-shaped section of the gutter 5 .
- the screen 9 comprises, similarly to the previous art, pairs of circular fuel passage orifices 10 , 10 ′, whereof the orifices 10 , 10 ′ are each in the angular extension, from the centre of the circle formed by the axial section of the manihold 6 , of an orifice 8 , 8 ′, respectively, of a pair of orifices 8 , 8 ′ of the manihold 6 .
- the orifices 10 , 10 ′ of the screen 9 have a greater diameter than the orifices 8 , 8 ′ of the manihold 6 , in order to compensate for the opening of the fuel jet 11 , 11 ′, respectively, as can be seen on FIG. 6 .
- the gutter 5 of the burner ring 4 includes, at its wall corresponding to the base of its U-shaped section, i.e. on the upstream side, a transversal undercut 12 which follows its generatrix.
- Such undercut 12 is in communication with the secondary flow channel 15 of the turbo-jet engine. The secondary air flow will therefore cool down the anti-radiation screen 9 via the transversal undercut 12 .
- Such undercut 12 may be in the form of a continuous undercut along the generatrix of the gutter 5 , with linking tabs between its external and internal edges, or may be replaced with a series of bores.
- the anti-radiation screen 9 of the invention differs from the screens of the previous art by the presence, at the same angular position as the pairs of orifices 10 , 10 ′, of upstream circular orifices 13 , for the ventilation of the zone situated between the manihold 6 and the screen 9 .
- the air of the secondary flow runs through the undercut of the gutter 5 and impacts the wall of the screen 9 on its upstream portion.
- the downstream portion of the screen facing the flame caught with the trailing edges of the walls of the gutter 5 , is cooled down by conduction.
- the screen 9 is hence cooled down properly and ensures thermal protection of the fuel manihold 6 .
- the air of the secondary flow runs through the undercut of the gutter 5 , then through the ventilation orifice 13 of the screen 9 .
- II will then cool down not only upstream portions of the screen 9 situated around the ventilation orifice 13 , but also the space between the manihold 6 and the screen 9 then, by circulating along such space, the downstream portion of the screen 9 .
- the downstream portion of the screen 9 in particular that situated between two orifices 10 , 10 ′, is hence cooled down, which enables to avoid the shortcomings mentioned above.
- the downstream portion of the screen 9 is cooled down in the zones of its orifices 10 , 10 ′, which was not possible with the screens of the previous art, since the conduction of heat from the upstream portion to the downstream portion could not take place, whereas both these portions were not connected continuously because of the orifices 10 , 10 ′.
- the space situated between the manihold 6 and the screen 9 is ventilated, in the zones including the orifices 10 , 10 ′. This is obtained by drilling a ventilation orifice 13 in the transversal plane, relative to the shape of the screen 9 , i.e. axial relative to the turbo-jet engine, of each of the pairs of orifices 10 , 10 ′ therein contained.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Processes For Solid Components From Exhaust (AREA)
Abstract
Description
- The invention relates to a turbo-jet engine including a re-heating channel of the primary gas flow, a burner ring and a protective screen of the fuel manihold of the burner ring. The invention also relates to a burner ring and a protective screen for the turbo-jet engine.
- Turbo-jet engines with after burner comprise generally from the upstream portion to the downstream portion, in the flow direction of the gases, one or several compressor stages, a combustion chamber, one or several turbine stages, a re-heating channel or after burner channel, and an ejection nozzle. The primary gas flow is compressed in the compressor stages, partakes of the combustion of the fuel in the combustion chamber, expands in the turbine stages and enables new combustion of fuel, thanks to the oxygen still present therein, in the re-heating channel before expanding in the ejection nozzle.
- The re-heating channel comprises generally, at input, flame holder arms, extending radially in the primary gas flow and comprises a fuel injector which sprays said fuel into the gas stream, downwardly. The fuel is ignited and the flames are, because of the sectional shape of the arms causing a depression, “held” in the walls of the arms.
- There may also be provided a burner ring, placed concentrically to the casing of the re-heating channel and operating along the same principle. The ring comprises generally an outer enclosure in the form of a gutter, including a U-shaped section, open downward of the re-heating channel, in the gas stream of the primary flow, wherein a fuel manihold is situated, of circular section, seen as an axial sectional view, whereof the purpose is to spray the fuel downward.
- Downstream of the manihold, the fuel is ignited, and the flame is held in the gutter of the ring because of the shape of the latter. Consequently, the re-circulations of gas in the enclosure of the gutter are re-circulations of very hot gases. For enhanced thermal protection, the fuel manihold is surrounded by an anti-radiation screen. Such screen includes fuel passage orifices, corresponding to orifices of the manihold, generally gathered in twos, in a same axial plane, at regular angular positions on the ring.
- For various profitability reasons, it has been attempted to increase the opening dimensions of the gutter. The re-circulation of the hot gases has been increased accordingly, and deformations, cracks and burns have been observed on the anti-radiation screen, in particular between the fuel passage orifices downstream of the screen “seeing” the flame. In such zones, the protection of the fuel manihold is consequently less efficient, thereby causing a risk of coking of the manihold.
- The purpose of the present invention is to improve the cooling process of the anti-radiation screen.
- To that effect, the invention relates to a double flow turbo-jet engine, including one or several compressor stages, a combustion chamber, one or several turbine stages, a re-heating channel of the primary flow and an ejection nozzle, the secondary flow emerging at least partially in the primary flow upstream of the re-heating channel, the re-heating channel including a burner ring, containing a flame holder gutter in the form of a ring portion whereof the upstream section is situated in the secondary flow, receiving a fuel manihold and a protective tubular screen of the manihold, characterised in that the gutter includes an upstream recess linked with the secondary flow, and the screen includes, on its upstream section, at least one ventilation orifice of the space situated between the screen and the manihold.
- Preferably, as the gutter includes an upstream recess linked with the secondary flow, the ventilation means comprise at least one ventilation orifice situated on the upstream portion of the screen.
- Advantageously in such a case, the manihold including at least one pair of fuel spraying orifices, the screen including at least one pair of corresponding orifices, a ventilation orifice is drilled on the screen at the same angular position as the pair of orifices.
- Advantageously still, as the screen includes a plurality of pairs of orifices, it comprises a ventilation orifice drilled at the same angular position of each pair of orifices.
- The invention also relates to a burner ring for a turbo-jet engine, including a flame holder gutter, a fuel manihold and a protective screen of the manihold, characterised in that it comprises the features of the ring described previously.
- The invention still relates to a protective screen of a burner ring manihold for a turbo-jet engine, characterised in that it comprises at least one pair of orifices and a ventilation orifice situated in the transversal plane of the pair of orifices.
- Preferably, the screen comprises a plurality of pairs of orifices and a ventilation orifice situated in the transversal plane of each pair of orifices.
- The invention will be understood better using the following description of the preferred embodiment of the turbo-jet engine of the invention, with reference to the appended drawings, whereon:
-
FIG. 1 shows a partial axial sectional view of the preferred embodiment of the turbo-jet engine of the invention, in the zone of the burner ring; -
FIG. 2 shows a partial cross-sectional view of the turbo-jet engine of the invention; -
FIG. 3 shows a perspective view of the fuel manihold of the burner ring of the turbo-jet engine of the invention; -
FIG. 4 shows a perspective view of the anti-radiation screen of the burner ring of the turbo-jet engine of the invention; -
FIG. 5 shows an axial sectional view of the burner ring of the turbo-jet engine of the invention, in a plane not including any pairs of orifices and -
FIG. 6 shows an axial sectional view of the burner ring of the turbo-jet engine of the invention, in a plane including a pair of orifices. - With reference to
FIG. 1 , the turbo-jet engine of the invention, extending globally along an axis A, comprises several compressor stages, a combustion chamber, several turbine stages, a re-heating channel of theprimary flow 1 and an ejection nozzle. - With reference to
FIG. 2 , at input of there-heating channel 1,fuel injector arms 2 extend radially, whereof the purpose is to spray fuel towards theflame holder arms 3, situated downstream of thefuel injector arms 2 and extending radially in there-heating channel 1. - By the flame holder
arms 3, the secondary flow, i.e. the cold air flow which has not run through the combustion chamber, emerges in the primary flow. Aferule 14 is placed upstream of thearms 3 and delineates asecondary flow channel 15. Downstream of thisferule 14, this secondary flow is mixed, at least partially, with the primary flow, in there-heating channel 1. - The number of
flame holder arms 3, nine in this case, is the same as that of thefuel injector arms 2 and are offset angularly relative to the latter, so that, on a front view, eachfuel injector arm 2 is situated between two consecutiveflame holder arms 3, equidistant therefrom. Thefuel injector arms 2 are radially smaller than theflame holder arms 3. - Close to the casing of the
re-heating channel 1, theflame holder arms 3 support aburner ring 4.Such ring 4 is made of a plurality of portions ofring 4′, here nine in number, extending concentrically to the casing of there-heating channel 1, between two successiveflame holder arms 3. It will be referred below to thering 4, by which is meant in fact a portion ofring 4′, and the constitutive elements of thering 4 will be in such a case elements constituting a portion ofring 4′, and therefore only extending on a truncated ring and not along a closed annular circumference. - The
fuel injector arms 2 extend radially, perpendicular to the axis of the turbo-jet engine. Theflame holder arms 3 extend radially, tilted downward, from their base, relative to the perpendicular to the axis of the turbo-jet engine contained in the axial plane of thearms 3. Thefuel injector arms 2 spray fuel downward. Theflame holder arms 3 do the same, and ensure moreover the ignition of the fuel and the catching of the flames by its outer walls, sized accordingly. - The
burner ring 4 includes aflame holder gutter 5, delineating its open external enclosure, which exhibits on an axial sectional view, a U-shaped section, whereof the legs are turned downward. The gutter extends along an annular direction, or generatrix. The external leg of the U is greater than the internal leg, and the legs of the U are not parallel; it rather looks like a rounded base V; it will be referred to later as a U-shaped section. - The
gutter 5 is placed outside, just downstream of theferule 14. Thus, the upstream wall forming the base of its U-shaped section is in contact with the secondary cold flow, as well as its downstream walls forming the legs of its U-shaped section, whereof the purpose is to catch the flames of there-heating channel 1, are subjected directly to the heat thereof. - With reference to
FIG. 3 , close to the base of the U, thegutter 5 receives afuel manihold 6, of circular section, seen as an axial sectional view and matching the circumferential shape of thegutter 5. Themanihold 6 is supplied with fuel by a longitudinal feeding ductwork 7, connected thereto from its upstream side. With reference toFIG. 6 , it comprises, arranged at regular angular positions, pairs ofcircular orifices orifices manihold 6, at the angular position of theorifices orifices fuel manihold 6. - With reference to
FIG. 4 , themanihold 6 is enveloped in aanti-radiation screen 9, of same tubular shape as themanihold 6 but whereof the section forms a circle of larger diameter, whereof the purpose is to protect themanihold 6 from the radiations of the flames situated downstream, here caught by the walls corresponding to the legs of the U-shaped section of thegutter 5. - The
screen 9 comprises, similarly to the previous art, pairs of circularfuel passage orifices orifices manihold 6, of anorifice orifices manihold 6. Theorifices screen 9 have a greater diameter than theorifices manihold 6, in order to compensate for the opening of thefuel jet FIG. 6 . - The
gutter 5 of theburner ring 4 includes, at its wall corresponding to the base of its U-shaped section, i.e. on the upstream side, atransversal undercut 12 which follows its generatrix.Such undercut 12 is in communication with thesecondary flow channel 15 of the turbo-jet engine. The secondary air flow will therefore cool down theanti-radiation screen 9 via thetransversal undercut 12.Such undercut 12 may be in the form of a continuous undercut along the generatrix of thegutter 5, with linking tabs between its external and internal edges, or may be replaced with a series of bores. - The
anti-radiation screen 9 of the invention differs from the screens of the previous art by the presence, at the same angular position as the pairs oforifices circular orifices 13, for the ventilation of the zone situated between themanihold 6 and thescreen 9. - With reference to
FIG. 5 , in a zone of theanti-radiation screen 9 not including anyorifices gutter 5 and impacts the wall of thescreen 9 on its upstream portion. The downstream portion of the screen, facing the flame caught with the trailing edges of the walls of thegutter 5, is cooled down by conduction. Indeed, in this orifice-free zone, there is continuity between the upstream portion and the downstream portion of thescreen 9; the cooling down effect provided by the impact of the upstream portion by the air of the secondary flow is therefore transmitted by conduction to its downstream portion. Thescreen 9 is hence cooled down properly and ensures thermal protection of thefuel manihold 6. - With reference to
FIG. 6 , in a zone of theanti-radiation screen 9 including a pair oforifices gutter 5, then through theventilation orifice 13 of the screen 9. II will then cool down not only upstream portions of thescreen 9 situated around theventilation orifice 13, but also the space between themanihold 6 and thescreen 9 then, by circulating along such space, the downstream portion of thescreen 9. The downstream portion of thescreen 9, in particular that situated between twoorifices - Thanks to the invention, the downstream portion of the
screen 9 is cooled down in the zones of itsorifices orifices manihold 6 and thescreen 9 is ventilated, in the zones including theorifices ventilation orifice 13 in the transversal plane, relative to the shape of thescreen 9, i.e. axial relative to the turbo-jet engine, of each of the pairs oforifices
Claims (8)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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FR0408153A FR2873408B1 (en) | 2004-07-23 | 2004-07-23 | TURBOREACTOR WITH A PROTECTION SCREEN OF THE FUEL RAMP OF A BURNER RING, THE BURNER RING AND THE PROTECTION SCREEN |
FR0408153 | 2004-07-23 |
Publications (2)
Publication Number | Publication Date |
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US20060016193A1 true US20060016193A1 (en) | 2006-01-26 |
US7574866B2 US7574866B2 (en) | 2009-08-18 |
Family
ID=34950697
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/177,297 Active 2027-01-02 US7574866B2 (en) | 2004-07-23 | 2005-07-11 | Turbo-jet engine with a protective screen of the fuel manifold of a burner ring, the burner ring and the protective screen |
Country Status (5)
Country | Link |
---|---|
US (1) | US7574866B2 (en) |
EP (1) | EP1619377B1 (en) |
CA (1) | CA2512377C (en) |
FR (1) | FR2873408B1 (en) |
RU (1) | RU2382895C2 (en) |
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US20070220893A1 (en) * | 2005-09-16 | 2007-09-27 | Woltmann Ivan E | Augmentor radial fuel spray bar with counterswirling heat shield |
US20070227152A1 (en) * | 2006-03-30 | 2007-10-04 | Snecma | Device for mounting an air-flow dividing wall in a turbojet engine afterburner |
US20100218505A1 (en) * | 2009-03-02 | 2010-09-02 | Snecma | Afterburner chamber for a turbomachine |
US20230228421A1 (en) * | 2020-06-26 | 2023-07-20 | Mitsubishi Heavy Industries, Ltd. | Fuel injector, combustor including the fuel injector, and gas turbine including the combustor |
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US7770381B2 (en) * | 2006-12-18 | 2010-08-10 | General Electric Company | Duct burning mixed flow turbofan and method of operation |
FR2950416B1 (en) * | 2009-09-23 | 2012-04-20 | Snecma | FLAME-APPARATUS DEVICE COMPRISING AN ARM SUPPORT AND A MONOBLOCS HEAT PROTECTION SCREEN |
US9303872B2 (en) * | 2011-09-15 | 2016-04-05 | General Electric Company | Fuel injector |
CN104373964B (en) * | 2014-10-20 | 2016-08-17 | 北京航空航天大学 | The cavity support plate flameholder of built-in beam hanger |
CN109654533B (en) * | 2018-12-04 | 2020-03-27 | 厦门大学 | Trailing edge air blowing type stabilizer adaptive to incoming flow distortion |
US11408610B1 (en) | 2021-02-03 | 2022-08-09 | General Electric Company | Systems and methods for spraying fuel in an augmented gas turbine engine |
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US4899539A (en) * | 1988-01-14 | 1990-02-13 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) | Flow mixer and flame stabilizer for a turbofan engine |
US5297391A (en) * | 1992-04-01 | 1994-03-29 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) | Fuel injector for a turbojet engine afterburner |
US5400589A (en) * | 1982-10-07 | 1995-03-28 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. | Afterburner for a turbofan engine |
US6112516A (en) * | 1997-10-23 | 2000-09-05 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) | Optimally cooled, carbureted flameholder |
US20070227151A1 (en) * | 2006-03-30 | 2007-10-04 | Snecma | Flameholder arm for an afterburner |
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DE1133185B (en) * | 1959-04-21 | 1962-07-12 | Snecma | Combustion device on recoil engines, especially for post-combustion |
FR1245920A (en) * | 1960-01-19 | 1960-11-10 | Le Ministre De La Defense Nati | Insulated fuel distribution manifold |
FR85730E (en) * | 1964-05-12 | 1965-10-01 | Snecma | Improvements to jet thruster combustion devices, particularly applicable to post-combustion |
FR2709342B1 (en) * | 1993-08-25 | 1995-09-22 | Snecma | Post combustion device of a turbojet engine. |
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- 2004-07-23 FR FR0408153A patent/FR2873408B1/en active Active
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2005
- 2005-06-30 EP EP05105972.3A patent/EP1619377B1/en active Active
- 2005-07-11 US US11/177,297 patent/US7574866B2/en active Active
- 2005-07-19 CA CA2512377A patent/CA2512377C/en active Active
- 2005-07-20 RU RU2005123135/06A patent/RU2382895C2/en active
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US5400589A (en) * | 1982-10-07 | 1995-03-28 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. | Afterburner for a turbofan engine |
US4899539A (en) * | 1988-01-14 | 1990-02-13 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) | Flow mixer and flame stabilizer for a turbofan engine |
US5297391A (en) * | 1992-04-01 | 1994-03-29 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) | Fuel injector for a turbojet engine afterburner |
US6112516A (en) * | 1997-10-23 | 2000-09-05 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) | Optimally cooled, carbureted flameholder |
US20070227151A1 (en) * | 2006-03-30 | 2007-10-04 | Snecma | Flameholder arm for an afterburner |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20070220893A1 (en) * | 2005-09-16 | 2007-09-27 | Woltmann Ivan E | Augmentor radial fuel spray bar with counterswirling heat shield |
US7596950B2 (en) * | 2005-09-16 | 2009-10-06 | General Electric Company | Augmentor radial fuel spray bar with counterswirling heat shield |
US20070227152A1 (en) * | 2006-03-30 | 2007-10-04 | Snecma | Device for mounting an air-flow dividing wall in a turbojet engine afterburner |
US7908868B2 (en) * | 2006-03-30 | 2011-03-22 | Snecma | Device for mounting an air-flow dividing wall in a turbojet engine afterburner |
US20100218505A1 (en) * | 2009-03-02 | 2010-09-02 | Snecma | Afterburner chamber for a turbomachine |
US8490402B2 (en) * | 2009-03-02 | 2013-07-23 | Snecma | Afterburner chamber for a turbomachine |
US20230228421A1 (en) * | 2020-06-26 | 2023-07-20 | Mitsubishi Heavy Industries, Ltd. | Fuel injector, combustor including the fuel injector, and gas turbine including the combustor |
Also Published As
Publication number | Publication date |
---|---|
RU2005123135A (en) | 2007-01-27 |
CA2512377C (en) | 2012-10-09 |
EP1619377B1 (en) | 2017-10-18 |
EP1619377A1 (en) | 2006-01-25 |
US7574866B2 (en) | 2009-08-18 |
FR2873408B1 (en) | 2008-10-17 |
CA2512377A1 (en) | 2006-01-23 |
RU2382895C2 (en) | 2010-02-27 |
FR2873408A1 (en) | 2006-01-27 |
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